Speaker
Description
In the frame of the French Space Operation Act (LOS) signed on 3rd June 2008, CNES is particularly interested by re-entries of space debris. CNES is indeed in charge of ensuring the right application of the law, for every mission launched or operated from the French territory. To predict the debris survivability during their re-entries and assess the prospective risk on ground, the development of complete multidisciplinary tools is required.
With this in mind, CNES develops its own spacecraft-oriented tool named PAMPERO since 2013. PAMPERO aims to simulate the complete atmospheric reentry of an entire satellite, launcher or the associated fragments due to the breakup process. These characteristics are the following:
- Six degrees-of-freedom flight dynamics,
- Aerodynamics and aerothermodynamics analysis : aerodynamics coefficients & parietal thermal heat fluxes computation,
- Heat transfers modeling by a 3D thermal conduction module,
- Mechanical stress analysis from the aerodynamic and thermal loads,
- Estimate of the destruction phenomena: ablation & fragmentation.
The purpose of this communication is to highlight the latest developments in the PAMPERO code, such as:
- New mesh generation and reading,
- Improvement of curvature radius computation (i.e planar surface issue),
- Aerodynamics coefficients and convective heat flux improvement for geometries where the modified Newton law is not relevant,
- Dumping effect issues,
- Coupling with the ASTER code, for mechanical stress analysis
- Taking into account multi-material objects,
- Fragmentation via predefined criteria.
Validation test-cases will be also presented.
